Lockheed Martin Skunk Works (LMSW) is currently developing a single-stage-to-orbit reusable launch vehicle called VentureStar(TM). The performance analyses that supported the initial studies were conducted to assess the effect of a lifting body shape, linear aerospike engine and metallic thermal protection system (TPS) on the weight and performance of the vehicle. These performance studies were performed in a multidisciplinary fashion that indirectly linked the trajectory optimization with weight estimation and aerothermal analysis tools. This approach was necessary to develop optimized ascent and entry trajectories that met all vehicle design constraints. Significant improvements in ascent performance were achieved when the vehicle flew a lifting trajectory and varied the engine mixture ratio during flight. Also, a considerable reduction in empty weight was possible by adjusting the total oxidizer-to-fuel and liftoff thrust-to-weight ratios. However, the optimal ascent flight profile had to be altered to ensure that the vehicle could be trimmed in pitch using only the flow diverting capability of the aerospike engine. Likewise, the optimal entry trajectory had to be tailored to meet TPS heating rate and transition constraints while satisfying a crossrange requirement.
Multidisciplinary Performance Analysis of a Lifting-Body Single-Stage-to-Orbit Vehicle
2000
14 pages
Report
No indication
English
Manned Spacecraft , Space Launch Vehicles & Support Equipment , Multidisciplinary design optimization , Lifting bodies , Single stage to orbit vehicles , Design analysis , Aerospike engines , Thermal analysis , Thermal protection , Trajectory optimization , Mixing ratios , Thrust-weight ratio , Reliability analysis , Aerothermodynamics , Ascent trajectories
A Multidisciplinary Performance Analysis of a Lifting-Body Single-Stage-to-Orbit Vehicle
British Library Conference Proceedings | 2000
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